Kwangwon Lee
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Previous Organizations / Institutes
The organizations / institutes from the scholar's other articles in the past ten years
Kwangwon Lee has a total of 19 co-authors. Here are the top co-authors by number of shared publications:
Sang-Young Park
6 shared publications- Chandeok Park
Department of Astronomy, Yonsei University, Seoul 03722, Republic of Korea
5 shared publications Chandeok Park
Yonsei University
4 shared publicationsHan-Earl Park
2 shared publicationsHyungjik Oh
2 shared publicationsDaesun Kim
Samsung Electronics Co., Ltd
1 shared publication
Latest Publications
- Open Access
Framework Development for Efficient Mission-Oriented Satellite System-Level Design
The space mission analysis and design process defines a space system at the system level to accomplish space mission objectives. Although the traditional process is well established and comprehensive through several years of experience, we propose a novel design process framework in this paper to aid the traditional process focusing on the following areas of improvement: (1) clarification of the direct connection between mission objectives and final system-level baseline design and requirements, (2) development of a comprehensive quantitative judgment criterion to evaluate various design alternatives, (3) derivation of system drivers and critical requirements after obtaining sufficient design knowledge based on the analysis of big data obtained from exploration of entire design space using an integrated design environment, and (4) system optimization even at the system level with a holistic perspective to guarantee that the baseline design meets the mission objectives. Examples of design steps in the proposed framework are characterizing stakeholder needs and engineering characteristics, building an integrated design environment, exploring and analyzing design space, optimizing system-level design, and elaborating mission utility to ensure an efficient mission-oriented design approach. The proposed framework is implemented in an example space mission involving quantum cryptographic communication. Accordingly, we demonstrate that the proposed framework provides an efficient mission-oriented satellite system-level baseline design.
Open AccessFramework Development for Efficient Mission-Oriented Satellite System-Level Design
The space mission analysis and design process defines a space system at the system level to accomplish space mission objectives. Although the traditional process is well established and comprehensive through several years of experience, we propose a novel design process framework in this paper to aid the traditional process focusing on the following areas of improvement: (1) clarification of the direct connection between mission objectives and final system-level baseline design and requirements, (2) development of a comprehensive quantitative judgment criterion to evaluate various design alternatives, (3) derivation of system drivers and critical requirements after obtaining sufficient design knowledge based on the analysis of big data obtained from exploration of entire design space using an integrated design environment, and (4) system optimization even at the system level with a holistic perspective to guarantee that the baseline design meets the mission objectives. Examples of design steps in the proposed framework are characterizing stakeholder needs and engineering characteristics, building an integrated design environment, exploring and analyzing design space, optimizing system-level design, and elaborating mission utility to ensure an efficient mission-oriented design approach. The proposed framework is implemented in an example space mission involving quantum cryptographic communication. Accordingly, we demonstrate that the proposed framework provides an efficient mission-oriented satellite system-level baseline design.
- 1 October 2019
- Published by Elsevier in Aerospace Science and Technology
- Vol. 93, 105298
Sub-optimal cooperative collision avoidance maneuvers of multiple active spacecraft via discrete-time generating functions
- 1 October 2019
- Published by Elsevier in Aerospace Science and Technology
- Vol. 93, 105298
Sub-optimal cooperative collision avoidance maneuvers of multiple active spacecraft via discrete-time generating functions
- 1 June 2018
- Published by Elsevier in Aerospace Science and Technology
- Vol. 77, 688-695
Real-time collision avoidance maneuvers for spacecraft proximity operations via discrete-time Hamilton–Jacobi theory
- 1 June 2018
- Published by Elsevier in Aerospace Science and Technology
- Vol. 77, 688-695
Real-time collision avoidance maneuvers for spacecraft proximity operations via discrete-time Hamilton–Jacobi theory
- 1 March 2017
- Published by Elsevier in Aerospace Science and Technology
- Vol. 62, 65-74
Near-optimal continuous control for spacecraft collision avoidance maneuvers via generating functions
- 1 March 2017
- Published by Elsevier in Aerospace Science and Technology
- Vol. 62, 65-74
Near-optimal continuous control for spacecraft collision avoidance maneuvers via generating functions
- Open Access
- 15 March 2016
- Published by The Korean Space Science Society in Journal of Astronomy and Space Sciences
- Vol. 33 (1) , 45-54
Improved GPS-based Satellite Relative Navigation Using Femtosecond Laser Relative Distance Measurements
- 15 March 2016
- Published by The Korean Space Science Society in Journal of Astronomy and Space Sciences
- Vol. 33 (1) , 45-54
Open AccessImproved GPS-based Satellite Relative Navigation Using Femtosecond Laser Relative Distance Measurements
- Open Access
- 15 December 2015
- Published by The Korean Space Science Society in Journal of Astronomy and Space Sciences
- Vol. 32 (4) , 387-393
Laser-based Relative Navigation Using GPS Measurements for Spacecraft Formation Flying
Laser-based Relative Navigation Using GPS Measurements for Spacecraft Formation Flying formation flying;global positioning system (GPS) measurement;laser measurement;relative navigation;extended Kalman filter (EKF); This study presents a precise relative navigation algorithm using both laser and Global Positioning System (GPS) measurements in real time. The measurement model of the navigation algorithm between two spacecraft is comprised of relative distances measured by laser instruments and single differences of GPS pseudo-range measurements in spherical coordinates. Based on the measurement model, the Extended Kalman Filter (EKF) is applied to smooth the pseudo-range measurements and to obtain the relative navigation solution. While the navigation algorithm using only laser measurements might become inaccurate because of the limited accuracy of spacecraft attitude estimation when the distance between spacecraft is rather large, the proposed approach is able to provide an accurate solution even in such cases by employing the smoothed GPS pseudo-range measurements. Numerical simulations demonstrate that the errors of the proposed algorithm are reduced by more than about 12% compared to those of an algorithm using only laser measurements, as the accuracy of angular measurements is greater than $0.001^{\circ}$ at relative distances greater than 30 km.- 15 December 2015
- Published by The Korean Space Science Society in Journal of Astronomy and Space Sciences
- Vol. 32 (4) , 387-393
Open AccessLaser-based Relative Navigation Using GPS Measurements for Spacecraft Formation Flying
Laser-based Relative Navigation Using GPS Measurements for Spacecraft Formation Flying formation flying;global positioning system (GPS) measurement;laser measurement;relative navigation;extended Kalman filter (EKF); This study presents a precise relative navigation algorithm using both laser and Global Positioning System (GPS) measurements in real time. The measurement model of the navigation algorithm between two spacecraft is comprised of relative distances measured by laser instruments and single differences of GPS pseudo-range measurements in spherical coordinates. Based on the measurement model, the Extended Kalman Filter (EKF) is applied to smooth the pseudo-range measurements and to obtain the relative navigation solution. While the navigation algorithm using only laser measurements might become inaccurate because of the limited accuracy of spacecraft attitude estimation when the distance between spacecraft is rather large, the proposed approach is able to provide an accurate solution even in such cases by employing the smoothed GPS pseudo-range measurements. Numerical simulations demonstrate that the errors of the proposed algorithm are reduced by more than about 12% compared to those of an algorithm using only laser measurements, as the accuracy of angular measurements is greater than $0.001^{\circ}$ at relative distances greater than 30 km. - 1 November 2015
- Published by ASM International
- Vol. 81030, 234-236
Analysis of Write Recovery Time Degradation Caused by Adjacent Storage Node Data in DRAM
As microelectronic feature sizes are scaled down, the characteristics and distribution of DRAM data retention time and write recovery time are getting worse. This degradation is due to the increases in the leakage current and resistance of the cell node and the decrease of cell capacitance in DRAM devices. As the physical distance between storage nodes decreases, node potential is increasingly affected by small potential changes in adjacent storage nodes. In this paper, we will show that the one of the most dominant contributors to failure is the adjacent storage node level, and we will demonstrate how node level affects write time delay. The effect of the adjacent storage node level can be correlated with a change in threshold voltage, much like the MOSFET body effect. We define this phenomenon as the lateral body effect, and propose a model for adjacent potential effect using the Buried Cell Array Transistor (BCAT) structure in sub 20nm DRAM.
- 1 November 2015
- Published by ASM International
- Vol. 81030, 234-236
Analysis of Write Recovery Time Degradation Caused by Adjacent Storage Node Data in DRAM
As microelectronic feature sizes are scaled down, the characteristics and distribution of DRAM data retention time and write recovery time are getting worse. This degradation is due to the increases in the leakage current and resistance of the cell node and the decrease of cell capacitance in DRAM devices. As the physical distance between storage nodes decreases, node potential is increasingly affected by small potential changes in adjacent storage nodes. In this paper, we will show that the one of the most dominant contributors to failure is the adjacent storage node level, and we will demonstrate how node level affects write time delay. The effect of the adjacent storage node level can be correlated with a change in threshold voltage, much like the MOSFET body effect. We define this phenomenon as the lateral body effect, and propose a model for adjacent potential effect using the Buried Cell Array Transistor (BCAT) structure in sub 20nm DRAM.
- 1 September 2014
- Published by Elsevier in Advances In Space Research
- Vol. 54 (6) , 1019-1028
Optimal tracking and formation keeping near a general Keplerian orbit under nonlinear perturbations
- 1 September 2014
- Published by Elsevier in Advances In Space Research
- Vol. 54 (6) , 1019-1028
Optimal tracking and formation keeping near a general Keplerian orbit under nonlinear perturbations